Bibliografías temáticas / Flame-shock interaction

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Literatura académica sobre el tema "Flame-shock interaction"

Autor: Grafiati

Publicado: 29 de marzo de 2025

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Artículos de revistas sobre el tema "Flame-shock interaction"

Dong, G., B. Fan, M. Gui y B. Li. "Numerical simulations of interactions between a flame bubble with an incident shock wave and its focusing wave". Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, n.º 10 (29 de junio de 2009): 2357–67. http://dx.doi.org/10.1243/09544062jmes1467.

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The numerical investigations of interactions between a flame bubble with an incident shock wave (IW) and its focusing wave (FW) in a reactive CH4—O2—N2 mixture are presented. The time-dependent, two-dimensional axisymmetric, reactive Navier—Stokes equations, with detailed chemical mechanisms, are employed to simulate the multiple shock—flame interactions process. The effects of the IW Mach number and chemical reactivity of mixture on flame structure and evolution are examined. The results of simulations show that the initial flame bubble can interact with IW, bow wave (BW), reflected BW, and FW in sequence. For the weak IW case, the repeated shock—flame interactions produce multiple Richtmyer—Meshkov (RM) instabilities that lead to the convolved flame with vortex structures, and the chemical heat release does not play a major role. While for the strong IW case, the multiple RM instabilities lead to the highly distorted flame with the complex vortices structures of large magnitude. With the lower reactive mixture, the instability process is the major mechanism for shock—flame interaction, while the chemistry only plays a minor role. However, with the higher reactive mixture, the distorted flame expands rapidly and finally forms the large-scale combustion through the interaction with FW. Both instability and chemical heat release play the important mechanisms in this case. The combustion acceleration in the highly reactive mixture can produce the stronger overpressure and the higher propagation speed of complex FW because of the chemi-acoustic interaction effect.

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Ju, Yiguang, Akishi Shimano y Osamu Inoue. "Vorticity generation and flame distortion induced by shock flame interaction". Symposium (International) on Combustion 27, n.º 1 (enero de 1998): 735–41. http://dx.doi.org/10.1016/s0082-0784(98)80467-0.

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Lutoschkin, E., M. G. Rose y S. Staudacher. "Pressure-Gain Combustion Using Shock–Flame Interaction". Journal of Propulsion and Power 29, n.º 5 (septiembre de 2013): 1181–93. http://dx.doi.org/10.2514/1.b34721.

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Yarkov, Andrey, Ivan Yakovenko y Alexey Kiverin. "Mechanism of Spontaneous Acceleration of Slow Flame in Channel". Fire 7, n.º 10 (10 de octubre de 2024): 362. http://dx.doi.org/10.3390/fire7100362.

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This paper is devoted to the numerical analysis of the spontaneous acceleration of a slow flame in a semi-closed channel. In particular, the flow development in the channel ahead of the propagating flame is analyzed. The applied detailed numerical model allows the clear observation of all features intrinsic to the reacting flow evolution in the channel, including the formation of perturbations on the scale of the boundary layer and their further development. In all considered cases, perturbations of the boundary layer emerge in the early stages of flame acceleration and decay afterward. The flow stabilizes more rapidly in a narrow channel, where the velocity profile is close to the Poiseuille profile. At the same time, the compression waves generated in the reaction zone travel along the channel. The interaction between compression waves in the area of combustion products can lead to the formation of shock waves. The effect of shock waves on the flow in the fresh mixture causes an increase in the flame area and a corresponding flame acceleration. In addition, shock waves trigger boundary-layer instability in wide channels. The perturbations of the boundary layer grow and evolve into vortexes, while further vortex–flame interaction leads to significant flame acceleration.

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KHOKHLOV, A., E. ORAN, A. CHTCHELKANOVA y J. WHEELER. "Interaction of a shock with a sinusoidally perturbed flame". Combustion and Flame 117, n.º 1-2 (abril de 1999): 99–116. http://dx.doi.org/10.1016/s0010-2180(98)00090-x.

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Fan, E., Weizong Wang y Tianhan Zhang. "Numerical investigation on flame dynamic and regime transitions during shock-cool flame interaction". Combustion and Flame 273 (marzo de 2025): 113928. https://doi.org/10.1016/j.combustflame.2024.113928.

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Thomas, Geraint, Richard Bambrey y Caren Brown. "Experimental observations of flame acceleration and transition to detonation following shock-flame interaction". Combustion Theory and Modelling 5, n.º 4 (diciembre de 2001): 573–94. http://dx.doi.org/10.1088/1364-7830/5/4/304.

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Roy, Christopher J. y Jack R. Edwards. "Numerical Simulation of a Three-Dimensional Flame/Shock Wave Interaction". AIAA Journal 38, n.º 5 (mayo de 2000): 745–54. http://dx.doi.org/10.2514/2.1035.

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Ivanov, M. F. y A. D. Kiverin. "Generation of high pressures during the shock wave–flame interaction". High Temperature 53, n.º 5 (septiembre de 2015): 668–76. http://dx.doi.org/10.1134/s0018151x15030086.

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Johnson, R. G., A. C. McIntosh, J. Brindley, M. R. Booty y M. Short. "Shock wave interaction with a fast convection-reaction driven flame". Symposium (International) on Combustion 26, n.º 1 (enero de 1996): 891–98. http://dx.doi.org/10.1016/s0082-0784(96)80299-2.

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Tesis sobre el tema "Flame-shock interaction"

La, Flèche Maxime. "Dynamics of Blast Wave and Cellular H2-Air Flame Interaction in a Hele-Shaw Cell". Thesis, Université d'Ottawa / University of Ottawa, 2018. http://hdl.handle.net/10393/38178.

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The present thesis investigates the interaction of a shock wave with a cellular flame and the ensuing mechanisms on the dynamics of the subsequent flame deformation. The inter- action is known to disrupt the flame surface through the Richtmyer-Meshkov instability, hence potentially enhancing the local combustion rates. This study aims to clarify the evolution of a flame when perturbed head-on by a shock wave. Two novel series of experiments were conducted in a vertically-oriented Hele-Shaw cell, which could successfully isolate a quasi-bidimensional cellular flame structure at ambient conditions. In the first configuration, the passage of the shock wave arising in the burned products of a deflagration wave was investigated, while both waves propagated in the same outward direction. In the other configuration, the shock wave centrally emerged in the unburned gases and collided with a cellular flame front traveling in the opposite direction. The event was captured using a Z-type Schlieren imaging system to visualize the growth of the flame cells. Shock characterization was determined in the Hele-Shaw apparatus to estimate the strength of the blast wave generated by energy deposition using a high-voltage igniter or by decoupled detonation from a detonation tube. A combustion study was also performed to determine the laminar flame speed in a mixture of hydrogen-air according to different equivalence ratios in the apparatus. The experiments revealed that inherent cellular flame instabilities are well developed in the observation scale of the Hele-Shaw geometry. The shock-flame complex was therefore analyzed experimentally for selected mixtures. As the shock wave traversed the interface separating the burned and unburned gases, the flame became more corrugated. Following the interaction, the flame cusps were stretched and/or flattened. At later times, the wrinkled interface was reversed and developed finer scales. A time scale analysis was performed to identify the contribution of the competing effects of Richtmyer-Meshkov and Rayleigh-Taylor instabilities on the flame interface deformation. For the case of a shock wave traversing the flame interface from the unburned to the burned side, the early perturbations were mainly governed by the Richtmyer-Meshkov instability. Finally, Rayleigh-Taylor instability resulted from the decaying pressure profile of the blast wave and tended to stabilize the perturbed interface to eventually reverse the cellular structure. Experimental and inert numerical results on the flame cell’s amplitude growth were found to be in good agreement.

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Lutoschkin, Eugen [Verfasser] y Martin G. [Akademischer Betreuer] Rose. "Pressure-gain combustion for gas turbines based on shock-flame interaction / Eugen Lutoschkin. Betreuer: Martin G. Rose". Stuttgart : Universitätsbibliothek der Universität Stuttgart, 2014. http://d-nb.info/105202100X/34.

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Yhuel, Emilie. "Simulation et analyse de l'interaction entre une flamme hydrogène/air et un choc incident". Electronic Thesis or Diss., Normandie, 2024. http://www.theses.fr/2024NORMIR44.

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La transition énergétique implique le développement de la filière hydrogène pour décarboner le transport et le stockage d’énergie. Toutefois, les propriétés de l’hydrogène compliquent son stockage et son transport comparé aux hydrocarbures, et sa sensibilité aux explosions représente un défi majeur en matière de sûreté. Pour mieux comprendre et maîtriser son comportement, des expériences et simulations numériques sont indispensables, utilisant des méthodes spécifiques pour capturer ces phénomènes complexes. Dans ce manuscrit, le code SiTCom-B a été employé pour simuler l’interaction d’une flamme hydrogène-air avec un choc incident (FSI), en vue de reproduire les résultats expérimentaux du laboratoire ICARE. Une première étude 2D dans un demi-canal (h/2 = 3.5 cm) a été menée pour analyser l’effet des conditions thermiques des parois et des modèles de diffusion. Un allumage plan avec chimie détaillée est simulé, aboutissant à la formation d’une flamme "tulipe". Un choc incident à Mach Ms = 1.4 ou 1.9 interagit ensuite avec la flamme. Les phénomènes observés dans la littérature sont reproduits : des instabilités apparaissent sur le front de flamme et aux parois, et une couche limite réactive se développe après la deuxième FSI. Des parois isothermes (300 K) et une chimie complexe sont conservées pour la suite des simulations. Dans un second temps, une étude paramétrique est réalisée en utilisant les dimensions exactes du canal expérimental (h = 4.5 cm, l = 2.1 cm). Deux types d’allumage (sphérique et plan) sont étudiés, conduisant à des flammes "doigt-de-gant" ou "tulipe". L’effet Soret est analysé et s’est avéré non-négligeable lors de la propagation de flamme d’hydrogène, tout comme l’impact de la gravité qui désymétrise la flamme et influence la FSI. Deux nombres de Mach sont considérés : Ms = 1.9 et 2.4. Une première étude 1D montre un auto-allumage suivi d’une détonation (DDT) pour Ms = 2.4, observée ensuite en 2D et 3D, mais plus tôt à cause des réflexions d’ondes de pression sur les parois latérales. Seule la simulation 3D permet de reproduire avec fidélité l’effet de ces réflexions. Pour Ms = 1.9, les simulations 2D révèlent une focalisation de choc et une accélération de la flamme, influencées par l’asymétrie initiale de celle-ci. Enfin, la FSI expérimentale d’une flamme en doigt-de-gant avec un choc à Ms = 1.9 est simulée en 3D, intégrant les observations précédentes. La vitesse de propagation et la courbure de la flamme sont reproduites avec précision. Les schlieren numériques correspondent également bien aux schlieren expérimentaux, validant ainsi les hypothèses de modélisation
The energy transition implies the development of the hydrogen sector to decarbonize energy transport and storage. However, hydrogen’s properties make it more difficult to store and transport than hydrocarbons, and its sensitivity to explosions represents a major safety challenge. To better understand and control its behavior, experiments and numerical simulations are essential, using specific methods to capture these complex phenomena. In this manuscript, the SiTCom-B code is used to simulate the interaction of a hydrogen-air flame with an incident shock (FSI), with the aim to reproduce experimental results from the ICARE laboratory. An initial 2D study in a half-channel (h/2 = 3.5 cm) has been carried out to analyze the effect of walls and diffusion models. A planar ignition with detailed chemistry is simulated, resulting in the formation of a “tulip” flame. An incident shock at Mach Ms = 1.4 or 1.9 then interacts with the flame. The phenomena observed in the literature are reproduced : instabilities appear on the flame front and at the walls, and a reactive boundary layer develops after the second FSI. Isothermal walls (300 K) and complex transport are retained for further simulations. In a second stage, a parametric study is carried out using the exact dimensions of the experimental channel (h = 4.5 cm, l = 2.1 cm). Two ignition types (spherical and planar) are studied, leading to “finger-glove” or “tulip” flames. The Soret effect is analyzed and is shown to be non-negligible during hydrogen flame propagation, as well as the gravity that de-symmetrizes the flame and influences the FSI. Two Mach numbers are considered : Ms = 1.9 and 2.4. An initial 1D study shows auto-ignition followed by detonation (DDT) for Ms = 2.4, then observed in 2D and 3D, but earlier due to pressure wave reflections on side walls. Only 3D simulations allows for capturing these reflections with exactitude. For Ms = 1.9, the 2D simulations reveal shock focusing and flame acceleration, influenced by the flame’s initial asymmetry. Finally, the experimental FSI of a finger-glove flame with a shock at Ms = 1.9 is simulated in 3D, incorporating the previous observations. Flame propagation velocity and curvature are accurately reproduced. The numerical schlieren also correspond well to the experimental schlieren, validating the modeling assumptions

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Paik, Kyong-Yup. "Experimental investigation of hot-jet ignition of methane-hydrogen mixtures in a constant-volume combustor". Thesis, 2016. https://doi.org/10.7912/C2XW8T.

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Indiana University-Purdue University Indianapolis (IUPUI)
Investigations of a constant-volume combustor ignited by a penetrating transient jet (a puff) of hot reactive gas have been conducted in order to provide vital data for designing wave rotor combustors. In a wave rotor combustor, a cylindrical drum with an array of channels arranged around the axis spins at a high rpm to generate high-temperature and high-pressure product gas. The hot-gas jet ignition method has been employed to initiate combustion in the channels. This study aims at experimentally investigating the ignition delay time of a premixed combustible mixture in a rectangular, constant-volume chamber, representing one channel of the wave rotor drum. The ignition process may be influenced by the multiple factors: the equivalence ratio, temperature, and the composition of the fuel mixture, the temperature and composition of the jet gas, and the peak mass flow rate of the jet (which depends on diaphragm rupture pressure). In this study, the main mixture is at room temperature. The jet composition and temperature are determined by its source in a pre-chamber with a hydrogen-methane mixture with an equivalent ratio of 1.1, and a fuel mixture ratio of 50:50 (CH4:H2 by volume). The rupture pressure of a diaphragm in the pre-chamber, which is related to the mass flow rate and temperature of the hot jet, can be controlled by varying the number of indentations in the diaphragm. The main chamber composition is varied, with the use of four equivalence ratios (1.0, 0.8, 0.6, and 0.4) and two fuel mixture ratios (50:50, and 30:70 of CH4:H2 by volume). The sudden start of the jet upon rupture of the diaphragm causes a shock wave that precedes the jet and travels along the channel and back after reflection. The shock strength has an important role in fast ignition since the pressure and the temperature are increased after the shock. The reflected shock pressure was examined in order to check the variation of the shock strength. However, it is revealed that the shock strength becomes attenuated compared with the theoretical pressure of the reflected shock. The gap between theoretical and measured pressures increases with the increase of the Mach number of the initial shock. Ignition delay times are obtained using pressure records from two dynamic pressure transducers installed on the main chamber, as well as high-speed videography using flame incandescence and Schileren imaging. The ignition delay time is defined in this research as the time interval from the diaphragm rupture moment to the ignition moment of the air/fuel mixture in the main chamber. Previous researchers used the averaged ignition delay time because the diaphragm rupture moment is elusive considering the structure of the chamber. In this research, the diaphragm rupture moment is estimated based on the initial shock speed and the longitudinal length of the main chamber, and validated with the high-speed video images such that the error between the estimation time and the measured time is within 0.5%. Ignition delay times decrease with an increase in the amount of hydrogen in the fuel mixture, the amount of mass of the hot-jet gases from the pre-chamber, and with a decrease in the equivalence ratio. A Schlieren system has been established to visualize the characteristics of the shock wave, and the flame front. Schlieren photography shows the density gradient of a subject with sharp contrast, including steep density gradients, such as the flame edge and the shock wave. The flame propagation, gas oscillation, and the shock wave speed are measured using the Schlieren system. An image processing code using MATLAB has been developed for measuring the flame front movement from Schlieren images. The trend of the maximum pressure in the main chamber with respect to the equivalence ratio and the fuel mixture ratio describes that the equivalence ratio 0.8 shows the highest maximum pressure, and the fuel ratio 50:50 condition reveals lower maximum pressure in the main chamber than the 30:70 condition. After the combustion occurs, the frequency of the pressure oscillation by the traversing pressure wave increases compared to the frequency before ignition, showing a similar trend with the maximum pressure in the chamber. The frequency is the fastest at the equivalence ratio of 0.8, and the slowest at a ratio of 0.4. The fuel ratio 30:70 cases show slightly faster frequencies than 50:50 cases. Two different combustion behaviors, fast and slow combustion, are observed, and respective characteristics are discussed. The frequency of the flame front oscillation well matches with that of the pressure oscillation, and it seems that the pressure waves drive the flame fronts considering the pressure oscillation frequency is somewhat faster. Lastly, a feedback mechanism between the shock and the flame is suggested to explain the fast combustion in a constant volume chamber with the shock-flame interactions.

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Donde, Pratik Prakash. "LES/PDF approach for turbulent reacting flows". 2012. http://hdl.handle.net/2152/19481.

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The probability density function (PDF) approach is a powerful technique for large eddy simulation (LES) based modeling of turbulent reacting flows. In this approach, the joint-PDF of all reacting scalars is estimated by solving a PDF transport equation, thus providing detailed information about small-scale correlations between these quantities. The objective of this work is to further develop the LES/PDF approach for studying flame stabilization in supersonic combustors, and for soot modeling in turbulent flames. Supersonic combustors are characterized by strong shock-turbulence interactions which preclude the application of conventional Lagrangian stochastic methods for solving the PDF transport equation. A viable alternative is provided by quadrature based methods which are deterministic and Eulerian. In this work, it is first demonstrated that the numerical errors associated with LES require special care in the development of PDF solution algorithms. The direct quadrature method of moments (DQMOM) is one quadrature-based approach developed for supersonic combustion modeling. This approach is shown to generate inconsistent evolution of the scalar moments. Further, gradient-based source terms that appear in the DQMOM transport equations are severely underpredicted in LES leading to artificial mixing of fuel and oxidizer. To overcome these numerical issues, a new approach called semi-discrete quadrature method of moments (SeQMOM) is formulated. The performance of the new technique is compared with the DQMOM approach in canonical flow configurations as well as a three-dimensional supersonic cavity stabilized flame configuration. The SeQMOM approach is shown to predict subfilter statistics accurately compared to the DQMOM approach. For soot modeling in turbulent flows, an LES/PDF approach is integrated with detailed models for soot formation and growth. The PDF approach directly evolves the joint statistics of the gas-phase scalars and a set of moments of the soot number density function. This LES/PDF approach is then used to simulate a turbulent natural gas flame. A Lagrangian method formulated in cylindrical coordinates solves the high dimensional PDF transport equation and is coupled to an Eulerian LES solver. The LES/PDF simulations show that soot formation is highly intermittent and is always restricted to the fuel-rich region of the flow. The PDF of soot moments has a wide spread leading to a large subfilter variance. Further, the conditional statistics of soot moments conditioned on mixture fraction and reaction progress variable show strong correlation between the gas phase composition and soot moments.
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Capítulos de libros sobre el tema "Flame-shock interaction"

Wang, C., Z. Z. Gu, R. L. Dong, L. T. Zhang, H. X. Jia y H. H. Shi. "Numerical Simulation on Detonation Formation by Shock/Flame Interaction". En 28th International Symposium on Shock Waves, 301–6. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-25688-2_45.

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Kiverin, A. D., M. F. Ivanov y M. A. Liberman. "Shock-Flame Interaction and Deflagration-to-Detonation Transition in Hydrogen/Oxygen Mixtures". En 28th International Symposium on Shock Waves, 325–30. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-25688-2_49.

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Billet, G., J. Ryan y M. Borrel. "Towards Direct Numerical Simulation of a Diffusion Flame-Shock Interaction with an AMR Algorithm". En Computational Fluid Dynamics 2006, 347–52. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-92779-2_53.

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Golub, V. V., D. I. Baklanov, S. V. Golovastov, K. V. Ivanov, M. F. Ivanov, A. D. Kiverin y V. V. Volodin. "Flame-Acoustic Interaction". En 28th International Symposium on Shock Waves, 273–79. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-25688-2_41.

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Zhao, Jianfu, Lei Zhou, Haiqiao Wei, Dongzhi Gao y Zailong Xu. "Experimental Investigation on the Flame-Shock Wave Interactions in a Confined Combustion Chamber". En 31st International Symposium on Shock Waves 2, 79–87. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_10.

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"Theory of Vorticity Generation by Shock Wave and Flame Interactions". En Dynamics of Shock Waves, Explosions, and Detonations, 429–48. New York: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/5.9781600865695.0429.0448.

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Actas de conferencias sobre el tema "Flame-shock interaction"

Hytovick, Rachel, Kenji Palavino, Jessica Chambers y Kareem Ahmed. "Video: Shock-Flame interaction with Bubble Explosion". En 71th Annual Meeting of the APS Division of Fluid Dynamics. American Physical Society, 2018. http://dx.doi.org/10.1103/aps.dfd.2018.gfm.v0092.

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Taylor, Brian, Ryan Houim, David Kessler, Vadim Gamezo y Elaine Oran. "Detonation Initiation and Shock-Flame Interaction in Hydrogen-Air Mixtures". En 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1171.

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Roy, Christopher y Jack Edwards. "Numerical simulation of a three-dimensional flame/shock wave interaction". En 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3210.

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Gundogdu, Birol y Martin G. Rose. "Pressure Gain Combustion by Using Shock Flame Interaction Pressure Rise". En ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15345.

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Abstract Pressure loss across a combustor in a gas turbine reduces thermal efficiency and increases specific fuel consumption. Theoretically, any pressure gain across the combustor results in higher thermal efficiency and lower specific fuel consumption. This work aims to obtain ‘time-averaged pressure rise across the combustor by using shock-flame interaction’. Multiple shock flame interaction increases the chemical heat release rate by two orders of magnitude. In this study, an impulsive heat addition for 30 microseconds with different heat release rates (10,30 and 100) is applied to a spherical zone within the primary zone of the combustor after a quasi-steady URANS combustion and the results are evaluated. A further study, the experimental part, will be based on shock flame interaction with different strengths of shocks. Inlet and outlet total pressures will be measured via high-pressure and high-temperature pressure transducers. Any pressure gain combustion can save billions of USD as gas turbines consume 13.9% of the total energy consumption.

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Huh, Hwanil, Jungyong Kim y James Driscoll. "Measured characteristics of flow and combustion in supersonic flame/shock wave interaction". En 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3935.

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Watanabe, Junya y Kenichi Takita. "Interaction Between Shock Waves, Hydrogen Flame and Plasma Jet in Supersonic Flow". En 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-7208.

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Bakalis, G., K. C. Tang Yuk, X. C. Mi, H. D. Ng y N. Nikiforakis. "Numerical modelling of detonation initiation via shock interaction with multiple flame kernels". En CENTRAL EUROPEAN SYMPOSIUM ON THERMOPHYSICS 2019 (CEST). AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5114012.

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Ishii, Kazuhiro, H. Shimomura y T. Tsuboi. "Interaction between a flame kernel and a shock wave generated by spark discharge". En 24th International Congress on High-Speed Photography and Photonics, editado por Kazuyoshi Takayama, Tsutomo Saito, Harald Kleine y Eugene V. Timofeev. SPIE, 2001. http://dx.doi.org/10.1117/12.424331.

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Wijeyakulasuriya, Sameera D., Manikanda Rajagopal y Razi Nalim. "Shock-Flame Interaction Modeling in a Constant-Volume Combustion Channel Using Detailed Chemical Kinetics and Automatic Mesh Refinement". En ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94617.

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More efficient and powerful gas turbine engines can be designed using constant-volume combustors that may involve ignition of a combustible mixture using a hot gas jet, subsequent flame and pressure-wave propagation, and their interactions. Accurate prediction of three-dimensional transient turbulent combustion is computationally challenging. To resolve propagating turbulent combustion, predict ignition, and track pressure waves accurately requires techniques to minimize the numerical cell count and kinetics calculation times. This study of shock-flame interaction (SFI) used detailed chemistry that includes low-temperature ignition reactions. Computational cells with similar temperatures and composition were grouped as ‘zones’ where kinetics are solved only once per zone per time step, using average values of species concentrations and thermodynamic properties for that zone. This avoids expensive kinetic calculations in every computational cell, with considerable speedup. A relatively coarser initial mesh was refined selectively and automatically, based on predicted velocity and temperature gradients, tracking propagating pressure waves and flames. The time step is variable, limited by the local speed of sound, to ensure accurate wave propagation. These techniques, previously validated for non-premixed, premixed and multiple-fuel turbulent combustion in industrial IC engines, are applied to study SFI during premixed combustion in a long constant-volume combustor.

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Farah, Hoden A., Frank K. Lu y Jim L. Griffin. "Numerical Simulation of Detonation Propagation in Flame Arrestor Applications". En ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23202.

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Abstract A detail numerical study of detonation propagation and interaction with a flame arrestor product was conducted. The simulation domain was based on the detonation flame arrestor validation test setup. The flame arrestor element was modeled as a porous zone using the Forchheimer equation. The coefficients of the Forchheimer equation were determined using experimental data. The Forchheimer equation was incorporated into the governing equations for axisymmetric reactive turbulent flow as a momentum sink. A 21-step elementary reaction mechanism with 10 species was used to model the stoichiometric oxyhydrogen detonation. Different cases of detonation propagation including inviscid, viscous adiabatic, and viscous with heat transfer and a porous zone were studied. A detail discussion of the detonation propagation and effect of the arrestor geometry, the heat transfer and the porous zone are presented. The inviscid numerical model solutions of the detonation propagation parameters are compared to one-dimensional analytical solution for verification. The viscous solutions are qualitatively compared to historical experimental data which shows very similar trend. The effect of the porous media parameters on shock transmission and re-initiation of detonation is presented.

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